JP5452634B2 - Fuel control method and fuel control apparatus for gas turbine combustor installed in gas turbine using high humidity air - Google Patents

Description

  The present invention relates to a fuel control method and a fuel control device for a gas turbine combustor installed in a gas turbine using high humidity air.

  A high-humidity air-based gas turbine power plant that improves output and efficiency by adding moisture to the gas turbine working fluid (air) and humidifying it, and recovering the thermal energy of the gas turbine exhaust gas with this humidified air Japanese Patent Laid-Open No. 2008-175098 discloses a fuel control means that can maintain flame stability while ensuring low NOx performance of a combustor before and after the start of humidification.

  In general, when the rotational speed rises when the gas turbine starts up, the compressor intake air flow rate and the vibration characteristics of the rotating body change, so that the operating state tends to become unstable due to disturbance compared to after reaching the rated rotational speed.

  In a high-humidity air-based gas turbine plant, if humidification is started while the rotation speed is increasing, disturbance will be given to the gas turbine. Therefore, in order to ensure stability at startup, after reaching the rated rotation speed It is desirable to start humidification in the partial load state.

  Nitrogen oxide (NOx) generated in the combustor is mostly thermal NOx generated by oxidation of nitrogen in the air when using a fuel having a low nitrogen content such as natural gas, kerosene, or light oil.

  Since the generation of thermal NOx is highly temperature-dependent, generally in gas turbines using these fuels, the reduction in flame temperature is the basic idea of the low NOx combustion method. As a measure for reducing the flame temperature, premixed combustion in which fuel and air are mixed in advance and then burned is known.

  Further, when the combustion air is heated by the regenerator as in a high-humidity air-utilizing gas turbine plant, the flame temperature is appropriately controlled while reducing the NOx reduction while preventing the spontaneous combustion of the fuel. A method for ejecting fuel and air as a large number of small-diameter coaxial jets into the combustion chamber is effective.

  In such a low NOx combustor, in order to achieve both low NOx performance and flame stability, it is important to adjust the fuel / air ratio, which is the ratio of the fuel flow rate to the air flow rate, within a predetermined range.

  Japanese Patent Application Laid-Open No. 7-189743 discloses a change in the opening degree of a compressor inlet guide valve, a change in air temperature, a change in air flow caused by a change in atmospheric pressure, a change in fuel temperature and a fuel heating value due to the operation of a gas turbine. Means for adjusting the ratio of the fuel flow rate to the air flow rate is disclosed for the change of the fuel flow rate.

  Japanese Patent Application Laid-Open No. 11-72029 discloses that in a gas turbine system that cools intake air of a compressor by intake air spray to reduce compression power, the fuel flow rate is increased or decreased according to the humidity of the air intake air and the amount of intake air spray water. Means are disclosed.

JP 2008-175098 A JP-A-7-189743 Japanese Patent Laid-Open No. 11-72029

  When humidification is started in a high-humidity air-utilizing gas turbine plant, the humidity of the combustion air in the combustor increases, so the combustion heat is lost to moisture, the flame temperature decreases, and the amount of NOx generated decreases. To do.

  Moreover, since the flow rate of the turbine working fluid increases due to the addition of moisture, the fuel flow rate decreases in order to keep the rotation speed constant. Decreasing the fuel flow rate lowers the flame temperature and reduces the amount of NOx generated. Furthermore, since the amount of heat recovered in the regenerator is reduced by lowering the flame temperature, the combustion air temperature is lowered. Lowering the combustion air temperature lowers the flame temperature and reduces the amount of NOx generated.

  Since humidification is started in this way, (1) increase in moisture, (2) decrease in fuel flow rate, and (3) decrease in air temperature progress simultaneously and the flame temperature decreases, so the amount of NOx generated is Although it decreases, the combustion stability deteriorates.

  If the combustion air flow rate is set low in consideration of humidification in advance, it is possible to prevent the flame from blowing out under high humidity conditions. However, in the combustor in which the combustor air distribution is set in this way, the flame temperature becomes high contrary to the above before the start of humidification, so that the stability of the flame is ensured but the NOx generation amount tends to increase. There is.

  That is, in a high-humidity air-utilizing gas turbine plant, a large change in conditions occurs with respect to NOx generation and flame stability of the combustor before and after the start of humidification. Further, it is considered that there is a delay until the moisture is actually added to the combustion air when the gas turbine is increased due to the valve control and the volume of the system after the start of humidification.

  At the time of gas turbine down load, it is considered that there is a delay until the humidity of the combustion air decreases for the same reason.

  When the combustion air humidity changes after a delay time with respect to the start and stop operation of the humidification operation, the flame temperature may become excessively high or low, so that a significant increase in NOx and a decrease in combustion stability occur. there is a possibility.

  Therefore, a control means for stably combusting the combustor with low NOx against such a change in conditions is required.

  Therefore, as disclosed in Japanese Patent Application Laid-Open No. 2008-175098, a part of the combustor including a plurality of combustors to which fuel is individually supplied is made more flame-holding than other combustors. Combustion temperature before the start of humidification is composed of an excellent combustion part (combustion part with air holes that give a swirl component to the air flow) As described above, the combustion stability after humidification can be ensured by the means for controlling the fuel by setting a large ratio of the fuel supplied to the combustion section having excellent flame holding properties.

  In order to ensure the stability of combustion by applying such means as disclosed in JP-A-7-189743 to such a change in humidity, the moisture in the combustion air is measured, It is conceivable to control the fuel flow rate based on this value.

  Here, it is considered to measure the humidity of combustion air with a humidity sensor.

  Considering the measurement position of moisture, first, moisture measurement at the humidifier outlet can be considered. However, since the air at the outlet of the humidifier is close to the dew point, there is a problem that measurement accuracy cannot be expected by measurement using a humidity sensor. Second, moisture measurement at the regenerator outlet can be considered. However, since the air at the outlet of the regenerator is as high as 450 ° C. or higher, the humidity sensor is required to have high heat resistance.

  Next, consider the performance required of a humidity sensor. The combustion state changes from moment to moment due to changes in moisture in the air. Therefore, the humidity sensor is required to measure moisture in the air with high responsiveness and control the fuel flow rate ratio to maintain stable combustion.

  As described above, there are many problems to measure the moisture in the air by the humidity sensor to control the combustion and to perform stable combustion.

  In Japanese Patent Laid-Open No. 11-72029, in a gas turbine system in which intake air of a compressor is cooled by an intake spray device to reduce compression power, changes in combustion air humidity due to changes in atmospheric humidity and intake spray water amount are disclosed. Means for stable combustion is disclosed.

  Since the high-humidity air-utilizing gas turbine disclosed in the prior art includes a humidifying device downstream of the compressor, not only the intake air spray of the compressor but also the combustion air humidity varies greatly depending on the humidification amount of the humidifying device. . Further, when the temperature and humidity of the compressor discharge air change depending on the operating conditions of the intake spray device, it is considered that the humidification amount in the humidifier also changes accordingly.

  However, in order to stably burn the gas turbine combustor of the gas turbine using high humidity air, the fuel of the gas turbine combustor is considered in consideration of both the moisture change due to the intake air spray of the compressor and the moisture change in the humidifier. The technology for controlling the flow rate has not been studied.

  In addition, it can be operated with high reliability without damaging the combustion stability of the gas turbine combustor before humidification, before and after humidification of the gas turbine using high-humidity air, and during humidification, and the amount of NOx generated is low regardless of the humidification state. A technology for controlling the fuel flow rate of a gas turbine combustor using high-humidity air that can be maintained at a level has not been studied.

  An object of the present invention is to use a high-humidity air-utilizing gas turbine that humidifies air with a spray-type humidifier, which can be operated with high reliability without impairing combustion stability before humidification, before and after humidification, and during humidification. An object of the present invention is to provide a fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine capable of maintaining the NOx generation amount at a low level regardless of the state, and a fuel control apparatus therefor.

  A fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine according to the present invention includes a compressor and a gas that burns fuel using the compressed air compressed by the compressor to generate combustion gas. A turbine combustor, a turbine driven by combustion gas generated in the gas turbine combustor, and a high-pressure humidifier equipped with a humidifier for humidifying the compressed air compressed by the compressor and supplied to the gas turbine combustor with spray water. A gas turbine combustor for a gas turbine using moisture air, wherein the gas turbine combustor includes a plurality of combustion sections configured by a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air. It is installed in a high-humidity air-utilizing gas turbine that controls the fuel ratio of the fuel supplied to each of the plurality of combustion sections of the gas turbine combustor based on the deviation between the load command and the power generation amount. In the fuel control method for a gas turbine combustor, a part of the combustion parts installed in the gas turbine combustor is formed into a combustion part having better flame holding properties than the other combustion parts. The flow rate of fuel to the combustion section of the gas turbine combustor is the amount of the combustion air supplied from the humidifier to the gas turbine combustor based on the amount of humidified water to the compressed air in the humidifier and the air temperature after humidification. The flow rate of fuel supplied to the combustion section with excellent flame holding properties formed in the gas turbine combustor based on the evaluation of the moisture content of the combustion air, and the fuel flow rate supplied to the other combustion sections The fuel ratio is controlled by adjusting the fuel ratio.

  The fuel control method for the gas turbine combustor installed in the high-humidity air-utilizing gas turbine of the present invention includes a compressor, an intake spray device that sprays water on the intake air at an intake portion of the compressor, and the compression A combustor that burns fuel using compressed air compressed by a compressor, a turbine driven by combustion gas from the combustor, and a spray-type humidifier that humidifies compressed air compressed by the compressor with spray water A gas turbine combustor for a high-humidity air-utilizing gas turbine provided with a device, the gas turbine combustor comprising a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air Installed in a high-humidity air-utilizing gas turbine that controls the fuel ratio of the fuel supplied to each of the multiple combustion sections of the gas turbine combustor based on the deviation between the load command and the power generation amount. In the fuel control method of a gas turbine combustor, among a plurality of combustion parts installed in the gas turbine combustor, a part of the combustion parts is formed in a combustion part having better flame holding properties than other combustion parts, The fuel flow rate to the combustion section of the gas turbine combustor is determined from the humidifier to the gas turbine based on the amount of humidified water in the intake spray device, the amount of humidified water to compressed air, and the air temperature after humidification by the humidifier. The amount of fuel supplied to the combustor is evaluated, and the flow rate of fuel supplied to the combustion portion having excellent flame holding properties formed in the gas turbine combustor based on the evaluation of the moisture content of the combustion air, and others Control is performed by adjusting the fuel ratio with the flow rate of fuel supplied to the combustion section.

  A fuel control apparatus for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine according to the present invention includes a compressor and a gas turbine that generates combustion gas by burning fuel using compressed air compressed by the compressor. High-humidity air comprising a combustor, a turbine driven by combustion gas generated in the gas turbine combustor, and a humidifier that humidifies the combustion air compressed by the compressor and supplied to the gas turbine combustor A gas turbine combustor for a use gas turbine, wherein the gas turbine combustor is provided with a plurality of combustion sections configured by a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air. And a high-humidity air-utilizing gas turbine that controls a fuel ratio of fuel supplied to each of the plurality of combustion sections of the gas turbine combustor based on a deviation between the load command and the power generation amount. In the fuel control apparatus for a turbine turbine combustor, among the plurality of combustion sections installed in the gas turbine combustor, a part of the combustion sections is configured as a combustion section having better flame holding properties than other combustion sections, and the gas A fuel control device for controlling the flow rate of fuel supplied to a plurality of combustion sections of a turbine combustor is a fuel supplied to a plurality of combustion sections of a gas turbine combustor based on a deviation between a load command MWD and an actual power generation amount MW. A fuel flow rate controller that outputs a fuel flow rate command for controlling the fuel flow rate, and a fuel ratio of fuel supplied to a plurality of combustion portions of the gas turbine combustor based on the fuel flow rate command output from the fuel flow rate controller, respectively Based on the fuel flow rate ratio setting device and the fuel flow rate setting value set by the fuel flow rate setting device, the flow rate ratios of the fuel supplied to the plurality of combustion sections of the gas turbine combustor are adjusted. An actual fuel flow rate controller for operating the fuel control valve, and further, a humidifier outlet maximum humidity calculator for calculating the maximum humidity of the humidifier outlet from the outlet air temperature of the humidifier, the amount of spray water of the humidifier and the humidifier A humidifier outlet humidity calculator that calculates the humidifier outlet humidity from the humidifier outlet maximum humidity calculated by the apparatus outlet maximum humidity calculator, the combustion air flow rate of the combustion air supplied to the gas turbine combustor, and the humidifier outlet humidity Combustion temperature F1 gain calculator for calculating the control gain for the combustion temperature and humidity for the fuel ratio of the fuel supplied to the combustion section of the gas turbine combustor having excellent flame holding properties from the humidifier outlet humidity calculated by the calculator And a humidity F1 gain calculator, and the fuel flow rate ratio is set based on the calculated values of the combustion temperature F1 gain calculator and the humidity F1 gain calculator. Among the combustion sections provided in the gas turbine combustor with a constant device, the fuel ratio of the fuel supplied to the combustion section having excellent flame holding properties is set, so that the plurality of combustion sections of the gas turbine combustor are set. It is characterized by controlling the flow rate of the supplied fuel.

  Further, a fuel control device for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine of the present invention generates a combustion gas by burning fuel using a compressor and compressed air compressed by the compressor. A high-humidity equipped with a gas turbine combustor, a turbine driven by combustion gas generated in the gas turbine combustor, and a humidifier that humidifies combustion air compressed by the compressor and supplied to the gas turbine combustor A gas turbine combustor for a split air-utilizing gas turbine, wherein the gas turbine combustor includes a plurality of combustion sections configured by a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air. Installed in a high-humidity air-utilizing gas turbine that controls the fuel ratio of the fuel supplied to each of the combustion sections of the gas turbine combustor based on the deviation between the load command and the power generation amount In the fuel control device for a gas turbine combustor, a part of the combustion parts installed in the gas turbine combustor is configured as a combustion part having a better flame holding property than other combustion parts, The fuel control device for controlling the flow rate of the fuel supplied to the plurality of combustion portions of the gas turbine combustor is supplied to the plurality of combustion portions of the gas turbine combustor based on the deviation between the load command MWD and the actual power generation amount MW. A fuel flow rate controller for outputting a fuel flow rate command for controlling the fuel to be controlled, and a fuel ratio of fuel supplied to a plurality of combustion portions of the gas turbine combustor based on the fuel flow rate command output from the fuel flow rate controller, respectively A fuel flow rate ratio setting device to be set, and a fuel flow rate ratio to be supplied to a plurality of combustion parts of the gas turbine combustor based on the fuel flow rate setting value set by the fuel flow rate setting device. An actual fuel flow rate controller for operating the fuel control valve to be adjusted, a humidifier outlet maximum water vapor amount calculator for calculating the maximum water vapor amount at the humidifier outlet from the outlet air temperature of the humidifier, and a spray of the humidifier Humidifier outlet water vapor amount calculator for calculating the humidifier outlet water vapor amount from the water amount and the humidifier outlet maximum water vapor amount calculated by the humidifier outlet maximum water vapor amount calculator, and the humidifier calculated by the humidifier outlet water vapor amount calculator A humidifier outlet humidity calculator for calculating the humidifier outlet humidity from the apparatus outlet water vapor amount, a combustion air flow rate of combustion air supplied to the gas turbine combustor, and a humidifier outlet humidity calculated by the humidifier outlet humidity calculator To calculate the control gain for the combustion temperature and humidity for the fuel ratio of the fuel supplied to the combustion section of the gas turbine combustor with excellent flame holding performance A firing temperature F1 gain calculator and a humidity F1 gain calculator are provided, and a plurality of the fuel flow rate ratio setters are provided in the gas turbine combustor based on the calculated values of the combustion temperature F1 gain calculator and the humidity F1 gain calculator. The flow rate ratio of the fuel supplied to the plurality of combustion portions of the gas turbine combustor is controlled by setting the fuel ratio of the fuel supplied to the combustion portion having excellent flame holding properties among the combustion portions. Features.

  Further, a fuel control device for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine of the present invention includes a compressor, an intake spray device that sprays water on the intake air at an intake portion of the compressor, and a compressor A gas turbine combustor that burns fuel using the compressed air compressed in step 1 to generate combustion gas, a turbine that is driven by the combustion gas generated in the gas turbine combustor, and the gas turbine combustion that is compressed by the compressor A gas turbine combustor for a high-humidity air-utilizing gas turbine equipped with a humidifying device for humidifying combustion air supplied to a combustor, the gas turbine combustor comprising a plurality of fuel nozzles for supplying fuel and combustion A plurality of combustion sections composed of a plurality of air flow paths for supplying industrial air are installed and supplied to the plurality of combustion sections of the gas turbine combustor based on the deviation between the load command and the power generation amount, respectively. In a fuel control apparatus for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine that controls the fuel ratio of the fuel, some of the combustion units installed in the gas turbine combustor A fuel control device that is configured as a combustion portion that has better flame holding properties than the combustion portion of the gas turbine and that controls the flow rate of fuel supplied to the plurality of combustion portions of the gas turbine combustor includes a load command MWD and an actual power generation amount MW. A fuel flow rate controller that outputs a fuel flow rate command for controlling the fuel supplied to the plurality of combustion portions of the gas turbine combustor based on the deviation from the gas flow rate, and a gas based on the fuel flow rate command output from the fuel flow rate controller A fuel flow rate ratio setting device for setting fuel ratios of fuel to be supplied to a plurality of combustion sections of the turbine combustor, and a gas flow rate ratio setting value set by the fuel flow rate ratio setting device. It has an actual fuel flow controller that operates a fuel control valve that adjusts the flow rate of fuel supplied to multiple combustion parts of the bin combustor, and calculates the maximum humidity at the outlet of the humidifier from the outlet air temperature of the humidifier The humidifier outlet maximum humidity calculator, the humidifier outlet humidity for calculating the humidifier outlet humidity from the humidifier spray amount and the spray water amount of the intake spray device and the humidifier outlet maximum humidity calculated by the humidifier outlet maximum humidity calculator Combustion part of the gas turbine combustor excellent in flame holding properties from the humidity calculator, the combustion air flow rate of the combustion air supplied to the gas turbine combustor, and the humidifier outlet humidity calculated by the humidifier outlet humidity calculator A combustion temperature F1 gain calculator and a humidity F1 gain calculator for calculating a control gain for the combustion temperature and humidity for the fuel ratio of the fuel supplied to Among the combustion sections provided in the gas turbine combustor with the fuel flow rate ratio setting device based on the calculated values of the combustion temperature F1 gain calculator and the humidity F1 gain calculator, The flow rate ratio of the fuel supplied to the plurality of combustion portions of the gas turbine combustor is controlled by setting the fuel ratio of the supplied fuel.

  Further, a fuel control device for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine of the present invention includes a compressor, an intake spray device that sprays water on the intake air at an intake portion of the compressor, and a compressor A gas turbine combustor that burns fuel using the compressed air compressed in step 1 to generate combustion gas, a turbine that is driven by the combustion gas generated in the gas turbine combustor, and the gas turbine combustion that is compressed by the compressor A gas turbine combustor for a high-humidity air-utilizing gas turbine equipped with a humidifying device for humidifying combustion air supplied to a combustor, the gas turbine combustor comprising a plurality of fuel nozzles for supplying fuel and combustion A plurality of combustion sections composed of a plurality of air flow paths for supplying industrial air are installed and supplied to the plurality of combustion sections of the gas turbine combustor based on the deviation between the load command and the power generation amount, respectively. In a fuel control apparatus for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine that controls the fuel ratio of the fuel, some of the combustion units installed in the gas turbine combustor A fuel control device that is configured as a combustion portion that has better flame holding properties than the combustion portion of the gas turbine and that controls the flow rate of fuel supplied to the plurality of combustion portions of the gas turbine combustor includes a load command MWD and an actual power generation amount MW. A fuel flow rate controller that outputs a fuel flow rate command for controlling the fuel supplied to the plurality of combustion portions of the gas turbine combustor based on the deviation from the gas flow rate, and a gas based on the fuel flow rate command output from the fuel flow rate controller A fuel flow rate ratio setting device for setting fuel ratios of fuel to be supplied to a plurality of combustion sections of the turbine combustor, and a gas flow rate ratio setting value set by the fuel flow rate ratio setting device. An actual fuel flow rate controller that operates a fuel control valve that adjusts the flow rate ratio of the fuel supplied to the plurality of combustion parts of the bin combustor is provided, and the maximum water vapor amount at the humidifier outlet is determined from the outlet air temperature of the humidifier. A humidifier outlet maximum water vapor amount calculator to calculate, a humidifier spray amount correction amount calculator to calculate a correction amount of the humidifier spray amount from the spray water amount of the intake spray device, a spray water amount of the humidifier and the humidifier outlet maximum A humidifier outlet water vapor amount calculator for calculating a humidifier outlet water vapor amount from a humidifier outlet maximum water vapor amount calculated by a water vapor amount calculator and a humidifier spray amount correction amount calculated by the humidifier spray amount correction amount calculator; Humidifier outlet humidity calculator that calculates the humidifier outlet humidity from the humidifier outlet steam quantity calculated by the humidifier outlet steam amount calculator, and combustion supplied to the gas turbine combustor Control of the fuel ratio of the fuel supplied to the combustion part of the gas turbine combustor having excellent flame holding performance from the combustion air flow rate of air and the humidifier outlet humidity calculated by the humidifier outlet humidity calculator with respect to the combustion temperature and humidity Combustion temperature F1 gain calculator and humidity F1 gain calculator for calculating gain respectively are provided, and gas turbine combustion is performed by the fuel flow rate ratio setter based on the calculated values of the combustion temperature F1 gain calculator and humidity F1 gain calculator. The ratio of the flow rate of the fuel supplied to the plurality of combustion parts of the gas turbine combustor by setting the fuel ratio of the fuel supplied to the combustion part having excellent flame holding properties among the plurality of combustion parts provided in the combustor It is characterized by controlling.

  According to the present invention, in a high-humidity air-utilizing gas turbine that humidifies air with a spray-type humidifier, it can be operated with high reliability without impairing combustion stability before humidification, before and after humidification, and during humidification. A fuel control method and a fuel control apparatus for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine capable of maintaining the NOx generation amount at a low level regardless of the state can be realized.

BRIEF DESCRIPTION OF THE DRAWINGS The block diagram which shows the high humidity air utilization gas turbine system provided with the gas turbine combustor which concerns on 1st Example of this invention. The fragmentary sectional view showing the structure of the fuel nozzle installed in the gas turbine combustor of 1st Example of this invention shown in FIG. The front view of the air hole plate which looked at the fuel nozzle installed in the gas turbine combustor of 1st Example of this invention shown in FIG. 2 from the combustion chamber. The characteristic view showing an example of the operating method of the high humidity air utilization gas turbine system provided with the gas turbine combustor of 1st Example of this invention. The characteristic view showing other examples of the operating method of the high-humidity air utilization gas turbine system provided with the gas turbine combustor of the 1st example of the present invention. The schematic diagram of the relationship between the amount of humidifier spray water and the humidifier outlet humidity in the high-humidity air-utilizing gas turbine system including the gas turbine combustor according to the first embodiment of the present invention. The schematic diagram (approximate line diagram) of the relationship between the humidifier spray water amount and the humidifier outlet humidity in the gas turbine system using the high humidity air provided with the gas turbine combustor of the first embodiment of the present invention. The characteristic view showing the further another example of the operating method in the high-humidity air utilization gas turbine system provided with the gas turbine combustor of 1st Example of this invention. The control block diagram which shows an example of the control apparatus which comprises the combustion control apparatus of the gas turbine combustor in the high-humidity air utilization gas turbine system of 1st Example of this invention. Explanatory drawing which shows one structure of F1 gain of F1 burner in the combustion control apparatus of the gas turbine combustor of 1st Example of this invention shown in FIG. The characteristic view showing an example of the operating method of the high humidity air utilization gas turbine system provided with the gas turbine combustor of 2nd Example of this invention. The schematic diagram of the relationship between the humidifier spray water amount and the humidifier outlet humidity in the high-humidity air-utilizing gas turbine system including the gas turbine combustor according to the second embodiment of the present invention. The control block diagram which shows an example of the control apparatus which comprises the combustion control apparatus of the gas turbine combustor in the high humidity air utilization gas turbine system of 2nd Example of this invention. The block diagram which shows the high-humidity air utilization gas turbine system provided with the gas turbine combustor which concerns on 3rd Example of this invention. The characteristic view showing an example of the operating method of the high humidity air utilization gas turbine system provided with the gas turbine combustor of 3rd Example of this invention. The characteristic view showing other examples of the operating method of the high-humidity air utilization gas turbine system provided with the gas turbine combustor of the 3rd example of the present invention. The schematic diagram of the relationship between the humidifier spray water amount and the humidifier outlet humidity in the gas turbine system using the high humidity air provided with the gas turbine combustor of the third embodiment of the present invention. The control block diagram which shows an example of the control apparatus which comprises the combustion control apparatus of the gas turbine combustor in the high humidity air utilization gas turbine system of the 3rd Example of this invention. The characteristic view showing an example of the operating method of the high-humidity air utilization gas turbine system provided with the gas turbine combustor of 4th Example of this invention. The schematic diagram of the relationship between the amount of humidification apparatus spray water and humidification apparatus exit humidity in the high-humidity air utilization gas turbine system provided with the gas turbine combustor of 4th Example of this invention. The control block diagram which shows an example of the control apparatus which comprises the combustion control apparatus of the gas turbine combustor in the high-humidity air utilization gas turbine system of 4th Example of this invention.

  A fuel control method and fuel control apparatus for a high-humidity air-utilizing gas turbine combustor according to an embodiment of the present invention will be described below with reference to the drawings.

  A fuel control method for a gas turbine combustor installed in a gas turbine using high humidity air according to a first embodiment of the present invention and a fuel control apparatus therefor will be described with reference to FIGS.

  FIG. 1 is an overall configuration of a high-humidity air utilization gas turbine system to which a fuel control method and a fuel control device for a gas turbine combustor installed in a high-humidity air utilization gas turbine according to a first embodiment of the present invention are applied. FIG.

  In the high-humidity air-utilizing gas turbine system shown in FIG. 1, the high-humidity air-utilizing gas turbine for power generation includes a compressor 1, a gas turbine combustor 2, a turbine 3, a humidifier 4, and a regenerator 5. The generator 20 is rotated by the output of the turbine 3 to obtain electric power.

  The gas turbine combustor 2 is stored in a combustor casing 6 and a combustor cover 7. A fuel nozzle 8 is provided at the center of the upstream end of the gas turbine combustor 2, and a substantially cylindrical combustor liner 9 that separates combustion air and combustion gas is provided downstream thereof.

  High-pressure air 102 obtained by compressing the gas turbine intake air 100 (atmospheric pressure) at the inlet of the compressor 1 with the compressor 1 flows through the gap between the transition piece 11 and the transition piece flow sleeve 12 to convectively cool the transition piece 11 and humidify it. Pre-hot air 103 is obtained.

  The pre-humidified high-temperature air 103 is supplied to the humidifier 4 to add moisture and become humidified air 104. The humidifier 4 humidifies the air by spraying spray water. Here, the humidified air 104 humidified by the humidifier 4 is under the water vapor saturation condition (relative humidity of 100% or less).

  In order to monitor the soundness of the high-humidity air-utilizing gas turbine, a thermometer for measuring the humidifier outlet temperature 500 is installed at the outlet of the humidifier 4.

  The humidified air 104 to which moisture has been added by the humidifier 4 is guided to the regenerator 5 and heated by heat exchange with the gas turbine exhaust gas 107 (turbine outlet low-pressure combustion gas).

  The heated humidified air 104 is injected into the combustor casing 6 as high-temperature and high-humidity air 105. Hot and humid air 105 in the combustor casing 6 flows through a generally annular space outside the combustor liner 9 toward the combustor head of the gas turbine combustor 2, and on the way, the combustor liner 9. Used for convection cooling.

  A part of the high-temperature and high-humidity air 105 flows into the combustor liner 9 from a cooling hole provided in the combustor liner 9 and is used for film cooling. The remaining high-temperature and high-humidity air 105 (36 in the A portion in the figure) flows into the combustor liner 9 from an air hole 32 described later, and burns in the gas turbine combustor 2 together with the fuel ejected from the fuel nozzle 31. And is sent to the turbine 3 as high-temperature combustion gas 106.

  The turbine outlet low-pressure combustion gas 107 exiting the turbine 3 is recovered by the regenerator 5 and becomes a regenerator outlet low-pressure combustion gas 108, which is exhausted from the exhaust tower 22 as exhaust gas 109.

  The driving force obtained by the turbine 3 is transmitted to the compressor 1 and the generator 20 through the shaft 21. Part of the driving force becomes air compression power in the compressor 1, and the remaining driving force is converted into electric power by the generator 20.

  The power generation amount MW, which is the output of the high-humidity air-utilizing gas turbine power plant, is calculated by the fuel flow rate adjustment valves 211 to 214 that calculate the flow rate of fuel supplied to the gas turbine combustor 2 based on the command signal from the control device 1000. Adjust and control opening and closing.

  The amount of water for humidifying the air by the humidifier 4 is controlled by adjusting the opening / closing of the humidifier spray water amount control valve 311 according to a command signal from the controller 1000.

  FIG. 2 is a view showing the structure of the fuel nozzle 9 of the gas turbine combustor 2 used in the high-humidity air-utilizing gas turbine of the present embodiment shown in FIG.

  A number of fuel nozzles 31 are attached to a fuel nozzle header 30 provided in the combustor cover 7 of the gas turbine combustor 2, and a number of air holes 32 corresponding to each one of the number of fuel nozzles 31 are provided. An air hole plate 33 is attached to the combustor cover 7 via a support 34.

  The air holes 32 formed in the pair of fuel nozzles 31 and the air hole plate 33 are substantially concentrically arranged, and as shown in detail in part A of FIG. Many coaxial jets of the jet 36 are formed.

  Due to the coaxial jet structure, the fuel and air are not mixed in the air holes 32 formed in the air hole plate 33. Therefore, even if the combustion air is at a high temperature as in a high-humidity air-utilizing gas turbine, the fuel is spontaneously ignited. Is not generated, and the air hole plate 33 is not melted, so that the gas turbine combustor 2 having high reliability can be obtained.

In addition, by forming a large number of such small coaxial jets, the interface between fuel and air is increased and mixing is promoted, so that the amount of NOx generated during combustion of the gas turbine combustor 2 can be suppressed.

  FIG. 3 is a view of the air hole plate 33 installed in the gas turbine combustor 2 of this embodiment as seen from the downstream side of the combustor. In the gas turbine combustor 2 of the present embodiment, a large number of air holes 32 (and fuel nozzles 31 that are paired with the air holes 32 (not shown)) extend from the radially inner periphery side to the radially outer periphery side of the air hole plate 33. Eight annular air hole arrays are arranged concentrically.

  As for the burner forming the combustion part of the gas turbine combustor 2, the four rows (first row to fourth row) on the center side are the F1 burner forming the combustion portion of the first group (F1), and the fifth row is the first row. The F2 burner forming the second group (F2) combustion part, the outer two rows (sixth and seventh rows) are the F3 burner forming the third group (F3) combustion part, and the outermost periphery (eighth row) are F4 burners that form the combustion section of the fourth group (F4) are divided into groups, and as shown in FIG. 2, flanges (51 to 51) provided on the header 30 for each group of F1 burners to F4 burners. 54), the fuel supplied from the fuel systems 201 to 204 provided with the flow control valves 211 to 214, respectively, is supplied to the fuel nozzle 31.

  Such a grouping structure of the fuel systems 201 to 204 enables fuel staging in which the number of fuel nozzles that supply fuel is changed in stages with respect to changes in the fuel flow rate of the gas turbine, and combustion stability during gas turbine partial load operation Securement and NOx reduction are possible.

  Further, the air holes 32 of the air hole plate 33 that constitutes the F1 burner forming the central four rows (F1) of the combustion parts are formed as oblique holes having an angle (α ° in FIG. 3) in the pitch circle tangential direction. Thus, the entire air flow flowing down this air hole 32 is swirled, and the flame is stabilized by the generated circulating flow.

  In the F2 burner to F4 burner disposed on the outer peripheral side of the F1 burner, the flame is stabilized by the combustion heat of the central F1 burner. Therefore, when humidification is started in the high-humidity gas turbine and the humidity of the combustion air increases, the flow rate of fuel supplied to the F1 burner of the gas turbine combustor 2 is increased, and the locally high-temperature portion is reduced. By providing, the combustion stability of F1 flame improves.

  Although the fuel flow rate of the burners after the F2 burner is reduced by the amount of increase in the F1 fuel, since these flames are stabilized by the combustion heat of the F1 burner, the combustion stability is ensured as a whole burner.

  An example of the operation method of the high-humidity air-utilizing gas turbine to which the fuel control method and fuel control device of the gas turbine combustor 2 of the present embodiment are applied will be described with reference to the characteristic diagrams shown in FIGS. To do.

  In the characteristic diagram of the operation method of the high-humidity air-utilizing gas turbine of FIG. 4, the horizontal axis is the time from the start of startup, and the vertical axis is the rotational speed, power generation amount, air flow rate, amount of spray water in the humidifier 4, humidifier from the top. 4 shows the outlet humidity 4 and the outlet temperature 500 of the humidifier 4.

  Further, in the characteristic diagram of the operation method of the high-humidity air-utilizing gas turbine of FIG. 5, the horizontal axis is the time from the start of startup as in FIG. 4, and the vertical axis is the combustion temperature of the gas turbine combustor 2 from the top, the gas turbine combustion 4 schematically represents the total fuel flow rate of the vessel 2 and the individual fuel flow rates (F1 flow rate to F4 flow rate) of the fuel systems 201 to 204 that supply fuel to the F1 burner to F4 burner.

4 and 5, the period a is the speed increase period from the start to the rated speed, and the period b is the combustion temperature after humidification, Tg, during the increased load period during the start of the gas turbine. _A period of ₁ or less, a period c is a period of time during which the combustion temperature after humidification is higher than the temperature Tg ₁ and higher than the temperature Tg ₁ in the increased load period during startup of the gas turbine, and is equal to or lower than the temperature Tg ₂ . The period d represents the load following operation period after the start is completed.

  The increasing load period b is further divided into a first moisture non-addition period b1, a moisture addition amount change period b2, and a moisture addition amount constant period b3. Here, the combustion temperature of the gas turbine combustor 2 is a value obtained from the fuel-air ratio (ratio of fuel flow rate to air flow rate), combustion air temperature, and combustion air humidity.

  In the operation method of the fuel control device of the gas turbine combustor 2 of the high-humidity air-utilizing gas turbine of the present embodiment, first, at the time of ignition and acceleration when the fuel flow rate is relatively small by a command from the control device 1000 of the fuel control device. Is operated by burning only the F1 burner located on the axial center side of the gas turbine combustor 2 (that is, supplying F1 fuel only to the fuel system 201 in FIG. 2), and the speed is increased to near the rated rotational speed no-load condition. . This single combustion of the F1 burner will be referred to as ¼ mode in the following description.

  Next, in the subsequent load increasing process (period b), F2 fuel is supplied to the F2 burner installed on the outer peripheral side of the F1 burner of the gas turbine combustor 2, and the operation is performed at F1 + F2. That is, by supplying F1 fuel and F2 fuel to the fuel systems 201 and 202 and adjusting the opening degree of the flow control valves 211 and 212 respectively installed in these fuel systems 201 and 202 according to a command from the control device 1000. The fuel flow rate of each F1 fuel and F2 fuel is controlled. This time is called a 2/4 mode.

  Next, the state in which F3 fuel is supplied to the fuel system 203 for supplying fuel to the F3 burner installed on the outer peripheral side of the F2 burner of the gas turbine combustor 2 and the F3 burner is ignited is called a 3/4 mode.

  In the process so far, moisture has not been added to the humidifier 4 of the high-humidity air-utilizing gas turbine (b1). That is, the humidifier water supply valve 311 for adjusting the flow rate of water supplied to the humidifier 4 of the high-humidity air utilizing gas turbine shown in FIG. 1 is fully closed, and the regenerative heat exchanger is changed depending on the opening degree of the humidifier bypass valve 312. The amount of water flowing through the feed water superheater 12 installed on the downstream side of 5 is controlled.

  Further, the increase in the fuel flow rate during this period is achieved by adjusting the opening degree of the flow rate control valves 211, 212, and 213 so that the gas turbine power generation amount increases according to the load increase rate determined in the start-up plan of the gas turbine. The fuel flow rates of the F1 fuel, F2 fuel, and F3 fuel supplied to the F2 burner and the F3 burner are controlled.

  Further, the fuel flow distribution of the F1 fuel, F2 fuel, and F3 fuel of each of the fuel systems 201 to 203 supplied to the F1 burner, the F2 burner, and the F3 burner is such that combustion of the gas turbine combustor 2 is stabilized and generated. Is supplied at a ratio determined so as to minimize.

  In the fuel control method and fuel control device of the gas turbine combustor 2 of the present embodiment, the addition of moisture to the humidifier 4 of the high-humidity air-utilizing gas turbine is started in this 3/4 mode. The air cooler-side humidifier water supply valve 312 installed in the humidifier 4 is opened by a command signal from the control device 1000 in response to a humidification start command, and water supply with a flow rate corresponding to the opening is injected into the humidifier 4 (period b2).

  At the same time, the air cooler side humidifier bypass valve 313 decreases the opening degree and finally controls the amount of water flowing through the air cooler 28 to be a predetermined value according to a command signal from the control device 1000. Fully closed state.

  Thereafter, the amount of water flowing through the air cooler 28 is adjusted to a predetermined value by controlling the opening degree of the air cooler-side humidifier water supply valve 312 (periods b2 to b3).

  At this time, the F1 burner, the F2 burner, and the F3 burner of the gas turbine combustor 2 are increased by the command signal from the control device 1000 so that the gas turbine power generation amount increases in accordance with the load increase rate determined in the gas turbine start-up plan. The fuel flow rate supplied to each is controlled. Of these, the F1 fuel supplied to the F1 burner plays a major role in ensuring combustion stability, so the ratio of the F1 flow rate to the total fuel flow rate is large after the start of humidification compared to before the humidification start to the humidifier 4. Need to be set to

  In the characteristic diagram of the operation method of the gas turbine system including the gas turbine combustor of the present embodiment shown in FIG. 5, the straight line portion indicated by the dotted line indicates the setting before humidification. In the gas turbine combustor 2 of the present embodiment, the fuel flow rate supplied to the F1 burner is indicated by a solid line with respect to the straight line portion indicated by the dotted line in order to prevent the total fuel flow rate from deviating from the plan. As described above, the fuel flow rate supplied to the F3 burner is set so as to decrease the F3 flow rate as shown by the solid line relative to the straight line portion shown by the dotted line by the amount corresponding to the increase in the F1 flow rate.

  For the determination of the optimum F1 flow rate for ensuring the combustion stability of the gas turbine combustor 2, judgment based on the F1 combustion temperature is effective.

  Of the various quantities necessary for calculating the combustion temperature, the combustion air humidity has a problem that it is difficult to directly measure in real time with a humidity sensor as described above.

Therefore, in the gas turbine combustor 2 of the present embodiment, the control device 1000 of the fuel control device causes the humidifier outlet that is the outlet humidity of the humidifier 4 from the humidifier spray water amount _{Gwh, sp} that is the amount of spray water to the humidifier 4. Consider evaluating the humidity Hm _{h and exit} .

Compared to the humidity measurement by the humidity sensor, the measurement of the humidifier spray water amount _{Gwh, sp} is easy at high speed and with high accuracy. Therefore, the humidifier spraying water _{G wh,} humidifier from _sp outlet humidity _{Hm h,} if evaluated _exit is one to one, the humidifier outlet humidity _{Hm h,} it is possible to real-time evaluation of the _exit.

When the residence time of the humidifier 4 is sufficiently secured, while the humidifier spray water amount _{Gwh, sp} is small, the air is easily humidified because it is away from the water vapor saturation condition, but the humidifier spray water amount _{Gwh, If the} amount of _sp becomes large, it is considered that air becomes difficult to be humidified because it approaches the water vapor saturation state.

In other words, when the humidifier spray water amount _{Gwh, sp} is infinite, the humidifier outlet humidity Hm _{h, exit} is considered to gradually approach the humidifier outlet maximum humidity Hm _{h, max} . Under ideal conditions, the humidifier outlet maximum humidity Hm _{h, max} is the saturation humidity Hm _{h, sat} at the humidifier outlet temperature 500.

FIG. 6 is a schematic diagram showing the relationship between the humidifier spray water amount _{Gwh, sp} and the humidifier outlet humidity Hmh _{, exit} to the humidifier 4. This relationship can be obtained by a measured value stored in a database or a calculation formula simulating humidification.

In the schematic diagram showing the relationship between the humidifier spray water amount of the humidifier 4 and the humidifier outlet humidity in the high-humidity air-utilizing gas turbine system in which the gas turbine combustor according to the first embodiment of the present invention is installed in FIG. When the humidifier spray water amount _{Gwh, sp} is increased, the humidifier outlet humidity Hmh _{, exit} is continuously increased.

Moreover, the relationship between the humidifier spray water amount of the humidifier 4 and the humidifier outlet humidity in the high-humidity air utilization gas turbine system including the gas turbine combustor according to the first embodiment of the present invention shown in FIG. 7 is shown. As shown in the schematic diagram (approximate line diagram), the humidifier outlet humidity Hm _{h, exit} is obtained with respect to the humidifier spray water amount G _{wh, sp} for several points of the humidifier outlet humidity Hm _{h, exit.} It is also possible to approximate with a straight line connecting the values of.

  If the combustion air humidity used in the control device 1000 installed in the fuel control device of the gas turbine combustor 2 of this embodiment shown in FIG. 9 is used, the combustion air temperature and the fuel-air ratio can be used in the gas turbine combustor 2. The combustion temperature can be calculated. By calculating the combustion temperature for the F1 burner with enhanced flame holding properties and comparing the F1 combustion temperature required for stable combustion, the F1 flow rate required for stable combustion can be obtained.

  In the control device 1000 installed in the fuel control device of the gas turbine combustor 2 of the present embodiment, the humidity calculation method is performed only during the period (period b3 in FIG. 4) in which the humidifier spray water amount 301 with respect to the humidifier 4 is constant. In addition, it is also effective in the period during which the humidifier water supply amount 301 changes (period b2 in FIG. 4). Therefore, combustion stability can be secured by setting the appropriate F1 flow rate even with respect to a transient humidity change of the combustion air due to a change in the amount of spray water 301 of the humidifier.

  FIG. 4 and FIG. 4 are characteristic diagrams showing another example of the operation method of the high-humidity air-utilizing gas turbine system including the gas turbine combustor according to the first embodiment of the present invention after reaching the planned humidification amount. 5 will be described.

In the gas turbine combustor 2 of the present embodiment, the combustion temperature reaches the temperature Tg ₁ when the fuel is increased in order to increase to a predetermined load with a constant humidification amount. If the local combustion temperature is higher than the NOx generation temperature, NOx is likely to be generated even in high humidity combustion.

Here, it is known from the result of the element combustion test that when the combustion temperature of the gas turbine combustor 2 is increased to some extent, it is possible to perform stable combustion of the gas turbine combustor 2 even with high humidity combustion. In the operation of the high-humidity air-utilizing gas turbine system in which the gas turbine combustor is installed, as shown in FIG. 5, when the combustion temperature of the gas turbine combustor 2 is equal to or higher than the temperature Tg ₁ , the gas turbine combustor has been increased until then. Gradually decrease the F1 flow rate and gradually increase the F3 flow rate.

When the combustion temperature of the gas turbine combustor 2 reaches the temperature Tg ₂ of the temperature higher than the temperature Tg _1, sets the F1 flow to local combustion temperature of F1 burners and F3 burner becomes equal.

As described above, in the period in which the combustion temperature of the gas turbine combustor 2 is equal to or higher than the temperature Tg ₁ and equal to or lower than the temperature Tg ₂ (the period c in FIGS. 4 and 5), the F1 flow rate is decreased contrary to the period b. By doing so, stable combustion of the gas turbine combustor 2 and further low NOx combustion can be realized in the full load range.

  FIG. 8 is a characteristic diagram showing still another example of the operation method in the high-humidity air-utilizing gas turbine system including the gas turbine combustor according to the first embodiment of the present invention, and the periods b2, b3, It is the figure which took out and expanded F1 flow volume and F3 flow volume about c.

  In the operation method of the high-humidity air-utilizing gas turbine system in which the gas turbine combustor according to the present embodiment shown in the characteristic diagram of FIG. 8 is installed, the straight line portion indicated by the dotted line is the F1 of the gas turbine combustor 2. The flow rate at which the combustion temperature of F3 is equivalent is shown, and the portion shown by the solid line is the operation corresponding to that shown in FIG.

In this characteristic shown in FIG. 8 diagrams that in the portions indicated by solid lines, humidifier humidifying start immediately to 4 is set higher F1 flow, secured in the period c combustion temperature is the temperature Tg ₁ more stable combustion In this stage, the fuel flow rate is controlled so that the combustion temperatures of F1 and F3 are equal.

If there is no problem in the combustion stability of the gas turbine combustor 2, simple flow rate control as indicated by a one-dot chain line is also possible. In the flow rate control indicated by the alternate long and short dash line, the flow rate control line can be determined simply by determining the F1 flow rate supplied to the F1 burner at the combustion temperature Tg ₁ of the gas turbine combustor 2, and control setting is easy.

  When the power generation amount or the turbine exhaust gas temperature reaches a predetermined amount, the start of the high-humidity air-utilizing gas turbine is completed, and thereafter, the high-humidity air-utilizing gas turbine is as shown in the characteristic diagram shown in FIG. The load follows the load by increasing or decreasing the flow rate of the fuel supplied to the gas turbine combustor 2 in accordance with the increase or decrease of the load (period d).

  During high-load operation of a high-humidity air-utilizing gas turbine, among the F1 burner to F4 burner installed in the gas turbine combustor 2, the fuel flow rate of F4 fuel supplied mainly to the outermost F4 burner is increased or decreased. To do. At this time, since the mixture of F4 fuel and air is mixed with the combustion gas from the F1 burner to the F3 burner and becomes high temperature, the oxidation reaction of the fuel proceeds slowly, and high combustion efficiency can be obtained.

  In addition, since the air distribution is set so that the temperature after the completion of combustion becomes equal to or lower than the temperature at which NOx generation becomes significant, combustion with almost zero NOx generation from the F4 burner becomes possible. Further, since the reaction is completed even with a very small amount of F4 fuel introduced into the F4 burner, continuous fuel switching is possible, and operability is improved.

  An example of a specific control block constituting the control device 1000 in the fuel control device of the gas turbine combustor 2 installed in the high-humidity air-utilizing gas turbine of this embodiment is shown in FIG.

  As shown in a specific control block constituting the control device 1000 installed in the fuel control device of the gas turbine combustor 2 installed in the high-humidity air-utilizing gas turbine of this embodiment shown in FIG. The difference between the load command MWD given so as to follow the generated power generation rate increase rate and the actual power generation amount MW is obtained by the subtractor 401 installed in the control device 1000, and the load command MWD obtained by the subtractor 401 and the actual power generation amount MW are obtained. A fuel flow rate command to the actual fuel flow rate controller 406 that controls the valve opening degree of the F1 fuel control valve 211 to F4 fuel control valve 214 supplied to the F1 burner to F4 burner of the turbine turbine combustor 2 based on the deviation from the power generation amount MW. A fuel flow controller 402 that calculates and outputs a value 410 is installed.

  The fuel flow rate command value 410 calculated by the fuel flow rate controller 402 installed in the control device 1000 becomes an input of the fuel flow rate ratio setting unit 403 installed in the control device 1000.

On the other hand, the humidifier outlet maximum humidity calculator 408 installed in the control device 1000 inputs the humidifier outlet temperature 500 measured by a thermometer installed at the outlet of the humidifier 4, and this humidifier maximum humidity calculator 408. humidifier outlet maximum humidity _{Hm h,} the _max calculated by the humidifier maximum humidity computing unit 408 with the calculated humidifier outlet maximum humidity _{Hm h,} and _max, are humidifier spraying water 301 sprayed onto the humidifier 4 The humidifier outlet humidity Hm _{h, exit} is calculated by the humidifier outlet humidity calculator 404 from the humidifier spray water amount _{Gwh, sp} .

The humidifier outlet humidity Hm _{h and exit} calculated by the humidifier outlet humidity calculator 404 are input to a humidity F1 gain calculator 405 and a combustion temperature F1 gain calculator 415 installed in the controller 1000, respectively.

The humidity F1 gain calculator 405 calculates an F1 gain with respect to humidity based on the humidity Hm _{h and exit} . The combustion temperature F1 gain calculator 415 generates a combustion from the combustion air flow rate, the fuel flow rate command value 410 calculated by the fuel flow rate controller 402, and the humidifier outlet humidity Hm _{h, exit} calculated by the humidifier outlet humidity calculator 404. Calculate F1 gain with respect to temperature.

  Then, the product of the output of the humidity F1 gain calculator 405 and the output of the combustion temperature F1 gain calculator 415 is obtained by a multiplier 416 installed in the control device 1000 to calculate the F1 gain 417, and this F1 gain 417 is controlled. Assume that the fuel ratio setting unit 403 installed in the apparatus 1000 is input.

  FIG. 10 schematically shows an example of the F1 gain 417 calculated by the multiplier 416 from the outputs of the humidity F1 gain calculator 405 and the combustion temperature F1 gain calculator 415 installed in the control apparatus 1000. FIG.

  As shown in FIG. 10, the F1 gain 417 for realizing the F1 flow rate shown in FIGS. 5 and 8 supplied to the F1 burner of the gas turbine combustor 2 can be calculated from the humidity and the combustion temperature.

  In order to achieve both low NOx and stable combustion in the gas turbine combustor 2 of the present embodiment, there are the following methods.

First, the F1 gain 417 is increased as the humidifier outlet humidity Hm _{h, exit} increases. By causing the F1 gain to follow the increase in humidity, stable combustion can be achieved.

After the humidification to the humidifier 4, after the combustion temperature of the gas turbine combustor 2 becomes equal to or higher than the combustion temperature Tg _{1 at} which stable combustion can be ensured, the local combustion temperatures of the F1 burner to F4 burner of the gas turbine combustor 2 The gas turbine combustor 2 is set such that the F1 gain is gradually decreased so that all the combustion temperatures of the F1 burner to the F4 burner of the gas turbine combustor 2 are equal to the combustion temperature Tg _{2 at} which they are equal. It is possible to achieve both low NOx and stable combustion.

Second, the F1 gain 417 is increased so that the F1 combustion temperature of the gas turbine combustor 2 becomes constant as the humidifier outlet humidity Hm _{h, exit} increases. Stable combustion and low NOx combustion of the gas turbine combustor 2 are set by setting the F1 gain 417 so that the F1 fuel flow rate is increased in accordance with the amount of increase in humidity so that the F1 combustion temperature becomes the same regardless of the humidity change. Can be achieved.

Then, setting the combustion temperature after humidification becomes combustion temperature Tg ₁ above, as the local combustion temperature of F1 burners ~F4 burner, gradually decrease the F1 gain 317 so that the equivalent to the combustion temperature Tg ₂ This makes it possible to achieve both low NOx and stable combustion in the gas turbine combustor 2.

Thirdly, the F1 gain 417 is increased so that the F1 combustion temperature of the gas turbine combustor 2 becomes higher as the humidifier outlet humidity Hm _{h, exit} increases. Depending on the combustion conditions, it is considered that the combustion stability decreases as the humidity increases.

  By setting the F1 gain 317 so that the F1 combustion temperature increases in accordance with the increase in humidity, the combustion stability of the gas turbine combustor 2 can be improved against humidity changes, and the reliability is further improved. .

Then, gradually from the combustion temperature after humidification becomes combustion temperature Tg ₁ or more, the local combustion temperature of F1 burners ~F4 burners of the gas turbine combustor 2, the F1 gain 317 so that the equivalent to the combustion temperature Tg ₂ By setting the gas turbine combustor so as to be small, both low NOx and stable combustion of the gas turbine combustor 2 can be achieved.

  Therefore, in the control device 1000 of the gas turbine combustor 2 of the present embodiment, as shown in FIG. 9, the fuel flow rate ratio setting device 403 installed in the control device 1000 is also installed in the control device 1000. Using the fuel flow rate command value 410 output from the fuel flow rate controller 402 as an input value, the fuel flow rate ratios (411 to 414) of F1 to F4 are calculated while referring to the value of the F1 gain 415.

  In the actual fuel flow rate controller 406 installed in the control apparatus 1000, the fuel flow rate ratios (411 to 414) of F1 to F4 calculated and output by the fuel flow rate ratio setting unit 403, and the fuel flow rate controller From the fuel flow rate command value 410 output from 402, the flow rate or valve opening of each fuel system of F1 to F4 is calculated and output to the fuel flow rate control valves 211 to 214, and the valve openings of the fuel flow rate control valves 211 to 214 are calculated. To control each.

  Thus, in the gas turbine combustor 2 of the present embodiment, it is possible to perform the fuel flow rate control as shown by the solid line in FIG. 5 by the control device 1000 having the configuration shown in FIG.

  Further, it is considered that there is a time delay until moisture is actually added to the combustion air after the start of humidification due to the valve control and the volume held by the system. At that time, if the actual combustion air humidity is estimated in consideration of the first-order lag with respect to the combustion air humidity, it is possible to achieve both NOx reduction and stable combustion of the gas turbine combustor 2.

  When the gas turbine is loaded, it is considered that a delay occurs until the combustion air humidity follows the humidifier spray water amount 301 in the humidifier 4 depending on the volume of the system such as the piping, which is particularly effective.

  Further, when the supply amount of spray water to the spray device 4 suddenly decreases or the supply of spray water is stopped for some reason, the combustion air humidity rapidly decreases, so the F1 combustion temperature of the gas turbine combustor 2 increases. It may be too much.

  According to the present embodiment, the combustion air humidity is estimated from the amount of supplied water, and fluctuations in the combustion air humidity can be detected. Therefore, the rapid increase in the F1 combustion temperature of the gas turbine combustor 2 can be avoided, and the reliability of the gas turbine. Will improve.

  Therefore, according to this embodiment, in a high-humidity air-utilizing gas turbine that humidifies air with a spray-type humidifier, it operates with high reliability without impairing combustion stability before humidification, before and after humidification, and during humidification. In addition, it is possible to realize a fuel control method for a high-humidity air-based gas turbine combustor and its fuel control apparatus that can maintain the NOx generation amount at a low level regardless of the humidified state.

  Next, a fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine according to a second embodiment of the present invention and its fuel control device will be described with reference to FIGS.

  The fuel control device of the gas turbine combustor installed in the high humidity air-utilizing gas turbine of this embodiment is installed in the high humidity air-utilizing gas turbine of the first embodiment of the present invention shown in FIGS. Since the basic configuration is the same as that of the gas turbine combustor fuel control apparatus, description of the configuration and operation common to both is omitted, and different portions will be described below.

  FIG. 11 is a characteristic diagram showing an example of the operation method of the high-humidity air-utilizing gas turbine of the second embodiment of the present invention, and the characteristic diagram of FIG. 11 corresponds to the characteristic diagram of FIG. 4 in the first embodiment. doing.

A fuel control device for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine according to this embodiment is a fuel control device for a gas turbine combustor installed in a high-humidity air-using gas turbine according to the first embodiment; the difference, rather than evaluating the humidifier outlet humidity of the humidifier 4 directly, first humidifier 4 humidifier outlet vapor quantity G _vh, seeking _exit, obtained the humidifier outlet vapor quantity G _vh, the _exit This is the point where the combustion air humidity is calculated.

By evaluating the combustion air humidity from the humidifier outlet water vapor amount G _{vh, exit} , the humidifier outlet humidity Hm _{h, exit} of the humidifier 4 can be evaluated with high accuracy.

FIG. 12 shows the relationship between the humidifier spray water amount _{Gwh, sp} and the humidifier outlet water vapor amount _{Gvh, exit} of the humidifier 4 in the high-humidity air utilization gas turbine system in which the gas turbine combustor according to this embodiment is installed. It is the shown schematic diagram. In the schematic diagram shown in FIG. 12, when the humidifier spray water amount _{Gwh, sp} increases, the humidifier outlet humidity Hm _{h, exit} is a curve that gradually approaches the humidifier outlet maximum humidity Hm _{h, max} .

Also in the high-humidity air-utilizing gas turbine system of the present embodiment, when the humidifier spray water amount _{Gwh, sp} increases _, as in the schematic diagram shown in FIG. 12, the humidifier outlet water vapor amount _{Gvh, exit} becomes humidified. It is considered asymptotic to the apparatus outlet maximum water vapor amount _{Gvh, max} .

Here, the humidifier outlet maximum water vapor amount G _{vh, max} of the humidifier 4 under ideal conditions is the saturated water vapor amount G _{vh, sat} with respect to the humidifier outlet flow rate and temperature. For example, the humidifier outlet water vapor amount G _{vh, exit} of the humidifier 4 is proportional to the humidifier outlet maximum water vapor amount G _{vh, max} and is multiplied by the unit amount, the humidifier spray water amount G _{wh, sp} and a negative proportional constant. It is given by a function that is proportional to the difference from the exponential function value with the value as a variable.

Specifically, the relationship between the humidifier spray water amount _{Gwh, sp} of the humidifier 4 and the humidifier outlet water vapor amount _{Gvh, exit} is expressed in the form as shown in Expression (1).

  Here, C is a constant.

  FIG. 13 is an example of a specific control block constituting the control device 1000 in the fuel control device of the gas turbine combustor 2 installed in the high-humidity air-utilizing gas turbine system of the present embodiment.

In the control device 1000 in the fuel control device of the gas turbine combustor 2 of the present embodiment shown in FIG. 13, the humidifier outlet maximum water vapor amount calculator 409 is a humidifier measured by a thermometer installed at the outlet of the humidifier 4. The outlet temperature 500 is input, the humidifier maximum steam amount calculator 409 calculates the humidifier outlet maximum steam amount _{Gvh, max} , and the humidifier maximum steam amount calculator 409 calculates the humidifier outlet maximum steam amount. From the amount G _{vh, max} and the humidifier spray water amount G _{wh, sp} which is the humidifier spray water amount 301 sprayed on the humidifier 4, the humidifier outlet steam amount G _vh of the humidifier 4 by the humidifier outlet steam amount calculator 407 is used. _{, Exit} is calculated.

The humidifier outlet water vapor amount G _{vh, exit} calculated by the humidifier outlet water vapor amount calculator 407 is input to the humidifier outlet humidity calculator 404. The configuration of the other control blocks is the same as that of the control device 1000 of the first embodiment shown in FIG.

  Thus, as in the first embodiment, the fuel control device for the gas turbine combustor installed in the high humidity air-utilizing gas turbine of this embodiment is capable of stable combustion against the constantly changing combustion air humidity. The required F1 gain can be obtained, and the humidity of the combustion air flowing into the gas turbine combustor can be evaluated with high accuracy. Therefore, highly reliable operation that achieves both low NOx and stable combustion more accurately. Can be realized.

  Therefore, according to this embodiment, in a high-humidity air-utilizing gas turbine that humidifies air with a spray-type humidifier, it operates with high reliability without impairing combustion stability before humidification, before and after humidification, and during humidification. In addition, it is possible to realize a fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine and a fuel control apparatus thereof that can maintain the NOx generation amount at a low level regardless of the humidified state.

  Next, a fuel control method for a gas turbine combustor installed in a gas turbine using high humidity air according to a third embodiment of the present invention and its fuel control device will be described with reference to FIGS.

  The fuel control device of the gas turbine combustor installed in the high humidity air-utilizing gas turbine of this embodiment is installed in the high humidity air-utilizing gas turbine of the first embodiment of the present invention shown in FIGS. Since the basic configuration is the same as that of the gas turbine combustor fuel control apparatus, description of the configuration and operation common to both is omitted, and different portions will be described below.

  FIG. 14 is a system flow diagram showing the overall configuration of the high humidity air-utilizing gas turbine system of the third embodiment of the present invention. The high humidity air-utilizing gas turbine system of the present embodiment is the high humidity of the first embodiment. The difference from the split air utilization gas turbine system is that the gas turbine intake air 100 is sprayed with water by the intake spray device 23 and compressed by the compressor 1 as the intake air 101 after water spray.

  In the high-humidity air-utilizing gas turbine system of the present embodiment, the compression power of the compressor 1 can be significantly reduced by spraying water on the intake air with the intake spray device 23.

  In the high-humidity air-utilizing gas turbine system of the present embodiment, the high-temperature air 103 before humidification flows into the humidifier 4 in a state of being humidified by the intake spray device 23, unlike the first embodiment. Therefore, how the humidity of the humidified air 104 humidified by the humidifier 4 changes with respect to the flow rate of the humidifier spray water 301 sprayed on the humidifier 4 when the pre-humidified high-temperature air 103 is already humidified. It is necessary to grasp what to do.

  Refer to the graphs of FIGS. 15 and 16 for an example of the operation method of the gas turbine system using the high humidity air to which the fuel control method and the fuel control device of the gas turbine combustor 2 of the present embodiment shown in FIG. 14 are applied. While explaining.

  In the characteristic diagram of the operation method of the high-humidity air-utilizing gas turbine in FIG. 15, the horizontal axis is the time from the start of the start as in FIG. 4, and the vertical axis is the rotational speed, power generation amount, air flow rate, spray water amount (humidifier) The spray water amount 301 and the compressor intake spray water amount 300), the humidifier outlet humidity of the humidifier 4 and the humidifier outlet temperature 500 of the humidifier 4 are shown.

  Further, in the characteristic diagram of the operation method of the high-humidity air-utilizing gas turbine of FIG. 16, the horizontal axis is the time from the start of startup as in FIG. 15, and the vertical axis is the combustion temperature of the gas turbine combustor 2 from the top, the gas turbine combustion 4 schematically represents the total fuel flow rate of the vessel 2 and the individual fuel flow rates (F1 flow rate to F4 flow rate) of the fuel systems 201 to 204 that supply fuel to the F1 burner to F4 burner.

  Further, in the characteristic diagrams of FIGS. 15 and 16, the period a is the speed increasing period from the start to the rated speed, the period b is the load increasing period during the start of the gas turbine, and the period c is the load after the end of the start. Represents the follow-up operation period.

  The increasing load period b includes a non-humidifying period b1, a humidifying amount changing period b2 of the humidifying device 4, a humidifying amount constant period b3 of the humidifying device 4, a spraying water amount changing period b4 of the intake spraying device 23, and a spraying water amount of the intake spraying device 23 Each is divided into a certain period b5.

  The period (humidity b1 to b3 in FIG. 4) from when humidification is started by the humidifier 4 until the humidification amount becomes constant is the same as that of the first embodiment of the present invention.

  In the operation method of the high-humidity air-utilizing gas turbine of this embodiment, after the humidification amount in the humidifier 4 becomes constant, the intake spray device 23 starts the intake spray. In response to the intake spray start command, the intake spray water amount control valve 310 is opened, water supply at a flow rate corresponding to the opening is supplied to the intake spray device 23, the intake spray water amount increases stepwise (period b4), and the spray water amount is a predetermined amount. It is adjusted to be a value (period b4 to b5).

  The gas turbine combustor 2 is stably combusted by increasing the F1 flow rate ratio of the gas turbine combustor 2 installed in the high-humidity air-utilizing gas turbine according to the present embodiment to increase the F1 combustion temperature. The system is the same as that of the first embodiment of the present invention.

Also in the operation method of the high-humidity air-utilizing gas turbine of the present embodiment, the first embodiment of the present invention is between the humidifier spray water amount _{Gwh, sp} of the humidifier 4 and the humidifier outlet humidity Hmh _{, exit.} Similar to the embodiment, a relationship similar to the schematic diagram shown in FIG. 6 is established.

FIG. 17 shows a schematic diagram of the relationship between the humidifier spray water amount _{Gwh, sp} of the humidifier 4 and the humidifier outlet humidity Hmh _{, exit} in the operation method of the gas turbine using the high humidity air of the present embodiment.

In the schematic diagram of FIG. 17, the humidifying device shown by the dotted line outlet humidity Hm _{h, exit} is humidifier outlet humidity Hm h in the case of there is an intake spray cooling _{is exit,} humidifier outlet humidity indicated by the solid line Hm _{h and exit} are humidifier outlet humidity Hm _{h and exit} when there is no intake spray cooling, and correspond to FIG. 6 according to the first embodiment of the present invention.

In the operation method of the high-humidity air-utilizing gas turbine of the present embodiment, since the high-temperature air 103 before humidification is humidified by the intake spray device 23, the humidifier spray water amount _{Gwh, sp} = 0 to the humidifier 4 is set. At this time, as shown by the dotted line in FIG. 17, the humidifier outlet humidity Hmh _{, exit} of the humidifier 4 does not become zero. That is, the humidifier outlet humidity Hm _{h, exit} when the humidifier spray water amount G _{wh, sp} = 0 is equal to the compressor outlet humidity Hmc _{, exit} .

Here, the compressor outlet humidity Hmc _{, exit} is a humidity change due to humidification from the compressor 1 intake section including the intake spray device 23 to the compressor 1 discharge section.

The relationship between the humidifier spray water amount _{Gwh, sp} and the humidifier outlet humidity Hmh _{, exit} of the humidifier 4 in the schematic diagram shown in FIG. 17 is a measured value or a database as in the case shown in FIG. Obtained by a formula that simulates humidification.

  An example of a specific control block constituting the control device 1000 in the fuel control device of the gas turbine combustor 2 installed in the high-humidity air-utilizing gas turbine of this embodiment is shown in FIG.

In the control device 1000, a different part from the control device in the fuel control device of the gas turbine combustor 2 of the first embodiment will be described. In the high-humidity gas turbine system including the intake spray device 23 upstream of the compressor 1, The compressor outlet humidity Hmc _{and exit} vary depending on the operating state of the intake spray device 23, that is, the intake spray water amount _{Gwc and wac} .

Therefore, in the control device 1000 of the present embodiment, the humidifier outlet maximum humidity calculator 408 inputs the humidifier outlet temperature 500 measured by a thermometer installed at the outlet of the humidifier 4 to calculate the humidifier maximum humidity. humidifier outlet maximum humidity _{Hm h} by vessel _408, calculates the _max, the humidifier maximum humidity computing unit 408 with the calculated humidifier outlet maximum humidity _{Hm h,} and _max, in the humidifier spraying water 301 sprayed onto the humidifier 4 By calculating the humidifier outlet humidity Hm _{h, exit} by the humidifier outlet humidity calculator 404 from a certain humidifier spray water quantity _{Gwh, sp} and the intake sprayer spray water quantity _{Gwc, wac} sprayed from the intake spray device 23 This corresponds to the fluctuation of the compressor outlet humidity Hmc _{and exit} .

Thus, the humidifier outlet humidity Hm _{h, exit} calculated by the humidifier outlet humidity calculator 404 takes into account not only the humidifier spray water amount G _{wh, sp} but also the intake spray device spray water amount G _{wc, sp.} By calculating the humidifier outlet humidity Hm _{h and exit} , the combustion air humidity can be evaluated with higher accuracy even in the case of a high humidity air-utilizing gas turbine equipped with the intake spray device 23. The configuration of the other control blocks is the same as that of the control device 1000 of the first embodiment shown in FIG.

  Thus, as in the first embodiment, the fuel control device for the gas turbine combustor installed in the high humidity air-utilizing gas turbine of this embodiment is capable of stable combustion against the constantly changing combustion air humidity. The required F1 gain can be obtained, and the humidity of the combustion air flowing into the gas turbine combustor can be evaluated with high accuracy. Therefore, highly reliable operation that achieves both low NOx and stable combustion more accurately. Can be realized.

  In the present embodiment, as shown in FIG. 15, the intake air spray in the intake spray device 23 is started after the humidification amount in the humidifier 4 is set to a constant amount. Then, humidification by the humidifier 4 can be started. Even in that case, the same fuel control method for the gas turbine combustor as in this embodiment can be applied. In summer when the atmospheric temperature rises, it is particularly effective to reduce the compression power by intake spray.

  Therefore, according to this embodiment, in a high-humidity air-utilizing gas turbine that humidifies air with a spray-type humidifier, it operates with high reliability without impairing combustion stability before humidification, before and after humidification, and during humidification. In addition, it is possible to realize a fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine and a fuel control apparatus thereof that can maintain the NOx generation amount at a low level regardless of the humidified state.

  Next, a fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine according to a fourth embodiment of the present invention and its fuel control apparatus will be described with reference to FIGS.

  The fuel control device for the gas turbine combustor installed in the high-humidity air-utilizing gas turbine of this embodiment is installed in the high-humidity air-utilizing gas turbine of the third embodiment of the present invention shown in FIGS. Since the basic configuration is the same as that of the gas turbine combustor fuel control apparatus, description of the configuration and operation common to both is omitted, and different portions will be described below.

  FIG. 19 is a characteristic diagram showing an example of the operation method of the high-humidity air-utilizing gas turbine of the fourth embodiment of the present invention, and the characteristic diagram of FIG. 19 corresponds to the characteristic diagram of FIG. 15 in the third embodiment. doing. The configuration of the high humidity air-utilizing gas turbine of the present embodiment is the same as the configuration of the high humidity air-utilizing gas turbine of the third embodiment shown in FIG.

The fuel control device of the gas turbine combustor installed in the high humidity air-utilizing gas turbine of the present embodiment is the fuel of the gas turbine combustor installed in the high humidity air-utilizing gas turbine of the third embodiment of the present invention. The difference from the control device is that the humidifying device outlet humidity of the humidifying device 4 is not directly evaluated as in the second embodiment of the present invention, but first, the humidifying device outlet water vapor amount G _{vh, exit} of the humidifying device 4 is determined. It is the point which calculated _| required and calculated the combustion air humidity from this calculated _| required humidification apparatus exit water vapor _| steam amount _{Gvh, exit} .

In the operation method of the high-humidity air-utilizing gas turbine of the present embodiment, as in the second embodiment of the present invention, the combustion air humidity is evaluated from the humidifying device outlet water vapor amount G _{vh, exit} , thereby _achieving high accuracy. The humidifier outlet humidity Hm _{h, exit} of the humidifier 4 is evaluated.

FIG. 20 shows the relationship between the humidifier spray water amount _{Gwh, sp} and the humidifier outlet steam amount _{Gvh, exit} of the humidifier 4 in the high-humidity air-utilizing gas turbine system in which the gas turbine combustor according to this embodiment is installed. It is the shown schematic diagram.

In the schematic diagram shown in FIG. 20, when the humidifier spray water amount _{Gwh, sp} increases, the humidifier outlet water vapor amount _{Gvh, exit} is a curve that gradually _{approaches the} humidifier outlet maximum water vapor amount _{Gvh, max} . .

In the schematic diagram of FIG. 20, dotted line indicated humidifier outlet vapor quantity G _{vh, exit} is humidifier outlet vapor quantity G _vh in the case of there is an intake spray cooling _{is exit,} humidifier shown by the solid line The outlet water vapor amount G _{vh, exit} is the humidifier outlet water vapor amount G _{vh, exit} when there is no intake spray cooling, and corresponds to FIG. 12 according to the second embodiment of the present invention.

In the operation method of the high-humidity air-utilizing gas turbine of the present embodiment, when the humidifier spray water amount _{Gwh, sp} increases _, as in the second embodiment of the present invention, the humidifier outlet water vapor amount _{Gvh, exit} is Asymptotic _{approach to the} maximum water vapor amount G _{vh, max} at the humidifier outlet. Under ideal conditions, the humidifier outlet maximum water vapor amount G _{vh, max} is the saturated water vapor amount G _{vh, sat} with respect to the humidifier outlet flow rate of the humidifier 4 and the outlet temperature 500 of the humidifier 4.

The operation method of the high-humidity air-utilizing gas turbine of this embodiment is the same as that of the third embodiment of the present invention. When the humidifier spray water amount G _{wh, sp} = 0, the humidifier outlet water vapor amount G _{vh, exit} of the humidifier 4 does not become zero as shown by the dotted line in FIG.

That is, the humidifier outlet water vapor amount _{Gvh, exit} when the humidifier spray water amount _{Gwh, sp} = 0 is equal to the compressor outlet water vapor amount _{Gvc, exit} .

Here, the compressor outlet water vapor amount G _{vc, exit} is the water vapor amount due to humidification from the compressor 1 intake portion including the intake spray device 23 to the compressor 1 discharge portion.

For example, the humidifier outlet water vapor amount G _{vh, exit} is proportional to the humidifier outlet maximum water vapor amount G _{vh, max} , the unit amount, the humidifier spray water amount G _{wh, sp} and the humidifier spray water amount correction amount G _{wh, sp_cor.} It is given by a function that is proportional to the difference from the exponential function value with the value obtained by multiplying the sum of and the negative proportionality constant as a variable. Specifically, the relationship between the humidifier spray water amount _{Gwh, sp} and the humidifier outlet water vapor amount _{Gvh, exit} is expressed in the form of the equation (2).

Here, C is a constant, and G _{wh and sp_cor} are correction terms that take into account the humidification amount in the intake spray device 23. That is, the humidifier spray water amount required when the humidifier 4 realizes the humidifier amount corresponding to the compressor outlet water vapor amount G _{vc, exit} is the humidifier spray water amount correction amount _{Gwh, sp_cor} .

  FIG. 21 shows an example of a specific control block constituting the control device 1000 in the fuel control device of the gas turbine combustor 2 installed in the high-humidity air-utilizing gas turbine of this embodiment.

In the control device 1000 of the fuel control device, a different part from the control device of the fuel control device of the second embodiment will be described. In this embodiment, the intake spray device spray water _{amounts Gwc and wac} sprayed from the intake spray device 23 are humidified. The apparatus spray water amount correction amount calculator 400 calculates the humidifier spray water amount correction amount _{Gwh, sp_cor} .

The humidifier outlet water vapor amount calculator 407 inputs the humidifier outlet temperature 500 and sprays the humidifier outlet maximum water vapor amount G _{vh, max} calculated by the humidifier outlet maximum water vapor amount calculator 409 with the humidifier 4. The humidifier outlet water vapor amount _{Gvh , exit} is calculated from the humidifier spray water amount _{Gwh , sp} and the humidifier spray water amount correction amount _{Gwh, sp_cor} calculated by the humidifier spray water amount correction amount calculator 400. The humidifier outlet water vapor amount G _{vh, exit} calculated by the outlet water vapor amount calculator 407 is input to the humidifier outlet humidity calculator 404 to calculate the humidifier outlet humidity Hm _{h, exit} .

Thus, not only the humidifier outlet maximum water vapor amount G _{vh, max} and the humidifier spray water amount G _{wh, sp} but also the humidifier spray water amount correction amount G _{wh, sp_cor} based on the intake spray device spray water amount G _{wc, sp} In consideration of the above, the humidifier outlet water vapor amount calculator 407 is configured to calculate the humidifier outlet maximum water vapor amount G _{vh, max,} thereby providing a high-humidity air-utilizing gas turbine provided with the intake spray device 23. However, the combustion air humidity can be evaluated with higher accuracy. The configuration of the other control blocks is the same as that of the control device 1000 of the second embodiment shown in FIG.

  Thus, as in the first embodiment, the fuel control device for the gas turbine combustor installed in the high humidity air-utilizing gas turbine of this embodiment is capable of stable combustion against the constantly changing combustion air humidity. The required F1 gain can be obtained, and the humidity of the combustion air flowing into the gas turbine combustor can be evaluated with high accuracy. Therefore, highly reliable operation that achieves both low NOx and stable combustion more accurately. Can be realized.

  Therefore, according to this embodiment, in a high-humidity air-utilizing gas turbine that humidifies air with a spray-type humidifier, it operates with high reliability without impairing combustion stability before humidification, before and after humidification, and during humidification. In addition, it is possible to realize a fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine and a fuel control apparatus thereof that can maintain the NOx generation amount at a low level regardless of the humidified state.

  The present invention is applicable to a fuel control method for a gas turbine combustor installed in a gas turbine using moisture air using high-humidity air, and its fuel control apparatus.

  1: compressor, 2: gas turbine combustor, 3: turbine, 4: humidifier, 5: regenerator, 6: combustor casing, 7: combustor cover, 8: fuel nozzle, 9: combustor liner, 10 : Liner flow sleeve, 11: transition piece, 12: transition piece flow sleeve, 20: generator, 21: shaft, 22: exhaust tower, 23: intake spray device, 30: fuel nozzle header, 31: fuel nozzle, 32: Air hole, 33: Air hole plate, 35: Fuel jet, 36: Air jet, 51: F1 fuel flange, 52: F2 fuel flange, 53: F3 fuel flange, 54: F4 fuel flange, 100: Gas turbine intake air, 101: Suction air after water spraying, 102: Compressed air, 103: High-temperature air before humidification, 104: Humidified air, 105: High-temperature high-humidity air, 106 High-temperature combustion gas, 107: Low pressure combustion gas at turbine outlet, 108: Low pressure combustion gas at regenerator outlet, 109: Exhaust pipe exhaust gas, 200: Fuel, 201: F1 fuel, 202: F2 fuel, 203: F3 fuel, 204: F4 Fuel 210: Fuel cutoff valve 211: F1 fuel control valve 212: F2 fuel control valve 213: F3 fuel control valve 214: F4 fuel control valve 300: Compressor intake spray water 301: Humidifier spray water 310: Compressor intake spray water amount control valve, 311: Humidifier spray water amount control valve, 320: Intake spray device drain, 321: Compressor internal drain, 322: Humidifier drain, 400: Humidifier spray water amount correction amount calculator 401: Subtractor 402: Fuel flow rate controller 403: Fuel flow rate ratio setting unit 404: Humidifier outlet humidity calculator 405: Humidity F1 gain setting , 406: Actual fuel flow controller, 407: Humidifier outlet water vapor amount calculator, 408: Humidifier outlet maximum humidity calculator, 409: Humidifier outlet maximum water vapor calculator, 410: Fuel flow command value, 411: F1 Fuel ratio, 412: F2 fuel ratio, 413: F3 fuel ratio, 414: F4 fuel ratio, 415: combustion temperature F1 gain setter, 416: multiplier, 500: humidifier outlet temperature, 1000: controller.

Claims (12)

A compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor to generate combustion gas, a turbine that is driven by the combustion gas generated by the gas turbine combustor, and a compressor A gas turbine combustor for a high-humidity air-utilizing gas turbine comprising a humidifier that humidifies compressed air supplied to the gas turbine combustor with spray water, the gas turbine combustor comprising fuel A plurality of combustion sections configured with a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air, and the plurality of combustion sections of the gas turbine combustor based on a deviation between a load command and a power generation amount In a fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine for controlling the fuel ratio of the fuel supplied to each of
Among the combustion parts installed in the gas turbine combustor, a part of the combustion parts is formed into a combustion part that has better flame holding properties than other combustion parts,
The fuel flow rate to the combustion section of the gas turbine combustor is the humidity of the combustion air supplied from the humidifier to the gas turbine combustor based on the amount of humidified water to the compressed air in the humidifier and the air temperature after humidification. The fuel flow rate supplied to the combustion portion having excellent flame holding properties formed in the gas turbine combustor based on the evaluation of the moisture content of the combustion air, and the fuel flow rate supplied to the other combustion portions A fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine, wherein the fuel ratio is controlled by adjusting the fuel ratio of the gas turbine. In the fuel control method of the gas turbine combustor installed in the high-humidity air-utilizing gas turbine according to claim 1,
Based on the increase in the moisture content of the combustion air humidified by the humidifier, the fuel ratio of the fuel to be supplied to the combustion part having excellent flame holding properties among the plurality of combustion parts installed in the turbine turbine combustor A fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine, characterized in that control is performed so that the amount of fuel increases compared to fuel supplied to a combustion section. In the fuel control method of the gas turbine combustor installed in the high-humidity air-utilizing gas turbine according to claim 2,
Based on the increase in the moisture content of the combustion air humidified by the humidifier, among the plurality of combustion parts installed in the turbine turbine combustor, the combustion temperature of the combustion part having excellent flame holding properties is constant. Installed in a high-humidity air-utilizing gas turbine, characterized in that the fuel ratio of the fuel supplied to the combustion part having excellent flame holding properties is controlled to be higher than the fuel supplied to the other combustion parts. A fuel control method for a gas turbine combustor. In the fuel control method of the gas turbine combustor installed in the high-humidity air-utilizing gas turbine according to claim 2,
Based on the increase in moisture content of the combustion air humidified by the humidifier, the temperature of the combustion part having excellent flame holding properties among the plurality of combustion parts installed in the turbine turbine combustor is increased. A gas turbine installed in a high-humidity air-utilizing gas turbine, characterized in that the fuel ratio of the fuel supplied to the combustion section having excellent flame resistance is controlled to be higher than the fuel supplied to the other combustion sections. Combustor fuel control method. In the fuel control method of the gas turbine combustor installed in the high-humidity air-utilizing gas turbine according to claim 1,
The amount of moisture in the combustion air is monotonically increasing with respect to the amount of humidified water in the compressed air, and as the amount of humidified water increases, the humidity of the combustion air is evaluated within the range of the upper limit of the humidity of the combustion air. A fuel for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine, characterized by controlling a fuel ratio of fuel supplied to the combustion section having excellent flame holding properties based on an evaluation of moisture content of air Control method. In the fuel control method of the gas turbine combustor installed in the high-humidity air utilization gas turbine according to any one of claims 2 to 4,
Combustion temperature of the combustion part excellent in flame holding property of the gas turbine combustor is provided with a first set temperature, and combustion temperature of the combustion part excellent in flame holding property is equal to or higher than the first set temperature. When the temperature is reached, the fuel ratio is adjusted so that the fuel ratio supplied to the combustion section having excellent flame holding performance is decreased within the range of the fuel ratio increased when the humidity of the combustion air is increased. A fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine. In the fuel control method of the gas turbine combustor installed in the high-humidity air-utilizing gas turbine according to claim 6,
The combustion temperature of the combustion section excellent in flame holding performance of the gas turbine combustor is provided with a second set temperature higher than the first set temperature, and the combustion temperature of the combustion section excellent in flame holding performance is When the second set temperature, which is higher than the first set temperature, is reached, the fuel ratio supplied to the combustion section having excellent flame holding properties is equivalent to the fuel ratio supplied to the other combustion sections. A fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine, wherein the fuel ratio is adjusted so that By a compressor, an intake spray device that sprays water on the intake air at an intake portion of the compressor, a combustor that burns fuel using the compressed air compressed by the compressor, and a combustion gas from the combustor A gas turbine combustor for a high-humidity air-utilizing gas turbine comprising a driven turbine and a spray-type humidifier that humidifies compressed air compressed by the compressor with spray water, the gas turbine combustor Installs a plurality of combustion sections composed of a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air, and a plurality of gas turbine combustors based on the deviation between the load command and the power generation amount In a fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine that controls a fuel ratio of fuel supplied to each combustion section,
Among the combustion parts installed in the gas turbine combustor, a part of the combustion parts is formed into a combustion part that has better flame holding properties than other combustion parts,
The fuel flow rate to the combustion section of the gas turbine combustor is determined from the humidifier based on the amount of humidified water in the intake spray device, the amount of humidified water to compressed air, and the air temperature after humidification by the humidifier. The flow rate of fuel supplied to the combustion portion having excellent flame holding properties formed in the gas turbine combustor based on the evaluation of the moisture content of the combustion air is evaluated based on the moisture content of the combustion air supplied to the turbine combustor. A fuel control method for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine, wherein control is performed by adjusting a fuel ratio with a fuel flow rate supplied to another combustion section. A compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor to generate combustion gas, a turbine driven by the combustion gas generated by the gas turbine combustor, and a compressor that compresses A gas turbine combustor for a high-humidity air-utilizing gas turbine provided with a humidifying device for humidifying combustion air supplied to the gas turbine combustor, wherein the gas turbine combustor supplies fuel A plurality of combustion sections each composed of a plurality of fuel nozzles and a plurality of air flow paths for supplying combustion air are installed, and each of the plurality of combustion sections of the gas turbine combustor is based on a deviation between a load command and a power generation amount. In a fuel control device for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine that controls the fuel ratio of the supplied fuel,
Among a plurality of combustion sections installed in the gas turbine combustor, a part of the combustion sections is configured as a combustion section having better flame holding properties than other combustion sections, and the plurality of combustion sections of the gas turbine combustor The fuel control device that controls the flow rate of the supplied fuel is:
A fuel flow rate controller that outputs a fuel flow rate command for controlling fuel supplied to a plurality of combustion sections of the gas turbine combustor based on a deviation between the load command MWD and the actual power generation amount MW, and an output from the fuel flow rate controller A fuel flow rate ratio setting device for setting a fuel ratio of fuel to be supplied to a plurality of combustion parts of the gas turbine combustor based on the fuel flow command, and a fuel flow rate setting value set by the fuel flow rate setting device An actual fuel flow rate controller for operating a fuel control valve that adjusts the flow rate ratio of the fuel supplied to the plurality of combustion portions of the gas turbine combustor based on
Further, from the humidifier outlet maximum humidity calculator that calculates the maximum humidity of the humidifier outlet from the outlet air temperature of the humidifier, from the amount of spray water of the humidifier and the humidifier outlet maximum humidity calculated by the humidifier outlet maximum humidity calculator The humidifying device outlet humidity calculator for calculating the humidifier outlet humidity, the combustion air flow rate of the combustion air supplied to the gas turbine combustor and the humidifier outlet humidity calculated by the humidifier outlet humidity calculator Are provided with a combustion temperature F1 gain calculator and a humidity F1 gain calculator for calculating a control gain for the combustion temperature and humidity with respect to the fuel ratio of the fuel supplied to the combustion section of the gas turbine combustor excellent in combustion. A plurality of combustion units provided in the gas turbine combustor with the fuel flow rate ratio setting device based on the calculation values of the calculator and the humidity F1 gain calculator. That is, the ratio of the fuel supplied to the plurality of combustion parts of the gas turbine combustor is controlled by setting the fuel ratio of the fuel supplied to the combustion part having excellent flame holding properties. A fuel control device for a gas turbine combustor installed in a gas turbine using moisture air. A compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor to generate combustion gas, a turbine driven by the combustion gas generated by the gas turbine combustor, and a compressor that compresses A gas turbine combustor for a high-humidity air-utilizing gas turbine provided with a humidifying device for humidifying combustion air supplied to the gas turbine combustor, wherein the gas turbine combustor supplies fuel A plurality of combustion sections each composed of a plurality of fuel nozzles and a plurality of air flow paths for supplying combustion air are installed, and each of the plurality of combustion sections of the gas turbine combustor is based on a deviation between a load command and a power generation amount. In a fuel control device for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine that controls the fuel ratio of the supplied fuel,
Among a plurality of combustion sections installed in the gas turbine combustor, a part of the combustion sections is configured as a combustion section having better flame holding properties than other combustion sections, and the plurality of combustion sections of the gas turbine combustor The fuel control device that controls the flow rate of the supplied fuel is:
A fuel flow rate controller that outputs a fuel flow rate command for controlling fuel supplied to a plurality of combustion sections of the gas turbine combustor based on a deviation between the load command MWD and the actual power generation amount MW;
A fuel flow rate setting unit that sets fuel ratios of fuel to be supplied to a plurality of combustion portions of the gas turbine combustor based on a fuel flow rate command output from the fuel flow rate controller, and a fuel flow rate ratio setting unit. An actual fuel flow rate controller for operating a fuel control valve that adjusts the flow rate ratio of the fuel supplied to the plurality of combustion portions of the gas turbine combustor based on the set value of the fuel flow rate ratio,
Further, the humidifier outlet maximum water vapor amount calculator for calculating the maximum water vapor amount at the humidifier outlet from the outlet air temperature of the humidifier, and the humidifier outlet calculated by the humidifier spray water amount and the humidifier outlet maximum water vapor amount calculator Humidifier outlet water vapor amount calculator for calculating the humidifier outlet water vapor amount from the maximum water vapor amount, and humidifier outlet humidity calculator for calculating the humidifier outlet humidity from the humidifier outlet water vapor amount calculated by the humidifier outlet water vapor amount calculator And the combustion air flow rate of the combustion air supplied to the gas turbine combustor and the humidifier outlet humidity calculated by the humidifier outlet humidity calculator to the combustion section of the gas turbine combustor with excellent flame holding properties A combustion temperature F1 gain calculator and a humidity F1 gain calculator for calculating a control gain for the combustion temperature and humidity for the fuel ratio of the fuel to be Of the combustion sections provided in the gas turbine combustor with the fuel flow rate ratio setting device based on the calculated values of the combustion temperature F1 gain calculator and the humidity F1 gain calculator, the combustion section having excellent flame holding properties. The fuel ratio of the fuel supplied to the gas turbine combustor is controlled by controlling the flow rate ratio of the fuel supplied to the plurality of combustion portions of the gas turbine combustor. Fuel control device for gas turbine combustor. A compressor, an intake spray device that sprays water on the intake air at an intake portion of the compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor and generates combustion gas, and a gas turbine Gas for a high-humidity air-utilizing gas turbine comprising a turbine driven by combustion gas generated in a combustor and a humidifying device that humidifies combustion air compressed by the compressor and supplied to the gas turbine combustor A turbine combustor, wherein the gas turbine combustor is provided with a plurality of combustion sections including a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air, and a load command and power generation amount The fuel control of the gas turbine combustor installed in the high-humidity air-utilizing gas turbine that controls the fuel ratio of the fuel supplied to each of the plurality of combustion sections of the gas turbine combustor based on the deviation from In the device,
Among a plurality of combustion sections installed in the gas turbine combustor, a part of the combustion sections is configured as a combustion section having better flame holding properties than other combustion sections, and the plurality of combustion sections of the gas turbine combustor The fuel control device that controls the flow rate of the supplied fuel is:
A fuel flow rate controller that outputs a fuel flow rate command for controlling fuel supplied to a plurality of combustion sections of the gas turbine combustor based on a deviation between the load command MWD and the actual power generation amount MW, and an output from the fuel flow rate controller A fuel flow rate ratio setting device for setting a fuel ratio of fuel to be supplied to a plurality of combustion parts of the gas turbine combustor based on the fuel flow command, and a fuel flow rate setting value set by the fuel flow rate setting device An actual fuel flow rate controller for operating a fuel control valve that adjusts the flow rate ratio of the fuel supplied to the plurality of combustion portions of the gas turbine combustor based on
Further, the humidifier outlet maximum humidity calculator that calculates the maximum humidity of the humidifier outlet from the outlet air temperature of the humidifier, the amount of spray water of the humidifier and the amount of spray water of the intake spray device, and the humidifier outlet maximum humidity calculator A humidifier outlet humidity calculator that calculates the humidifier outlet humidity from the maximum humidifier outlet humidity, and a humidifier outlet that calculates the combustion air flow rate of the combustion air supplied to the gas turbine combustor and the humidifier outlet humidity calculator A combustion temperature F1 gain calculator and a humidity F1 gain calculator for calculating a control gain for the combustion temperature and humidity for the fuel ratio of the fuel supplied to the combustion section of the gas turbine combustor having excellent flame holding properties from the humidity are provided. Based on the calculated values of the combustion temperature F1 gain calculator and the humidity F1 gain calculator, the fuel flow rate ratio setter performs gas turbine combustion. Among the plurality of combustion sections provided in the above, the fuel ratio of the fuel supplied to the combustion section having excellent flame holding properties is set, and the flow rate ratio of the fuel supplied to the plurality of combustion sections of the gas turbine combustor is set. A fuel control device for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine. A compressor, an intake spray device that sprays water on the intake air at an intake portion of the compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor and generates combustion gas, and a gas turbine Gas for a high-humidity air-utilizing gas turbine comprising a turbine driven by combustion gas generated in a combustor and a humidifying device that humidifies combustion air compressed by the compressor and supplied to the gas turbine combustor A turbine combustor, wherein the gas turbine combustor is provided with a plurality of combustion sections including a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air, and a load command and power generation amount The fuel control of the gas turbine combustor installed in the high-humidity air-utilizing gas turbine that controls the fuel ratio of the fuel supplied to each of the plurality of combustion sections of the gas turbine combustor based on the deviation from In the device,
Among a plurality of combustion sections installed in the gas turbine combustor, a part of the combustion sections is configured as a combustion section having better flame holding properties than other combustion sections, and the plurality of combustion sections of the gas turbine combustor The fuel control device that controls the flow rate of the supplied fuel is:
A fuel flow rate controller that outputs a fuel flow rate command for controlling fuel supplied to a plurality of combustion sections of the gas turbine combustor based on a deviation between the load command MWD and the actual power generation amount MW, and an output from the fuel flow rate controller A fuel flow rate ratio setting device for setting a fuel ratio of fuel to be supplied to a plurality of combustion parts of the gas turbine combustor based on the fuel flow command, and a fuel flow rate setting value set by the fuel flow rate setting device An actual fuel flow rate controller for operating a fuel control valve that adjusts the flow rate ratio of the fuel supplied to the plurality of combustion portions of the gas turbine combustor based on
Further, a humidifier outlet maximum water vapor amount calculator that calculates the maximum water vapor amount at the humidifier outlet from the outlet air temperature of the humidifier, and a humidifier spray amount that calculates the correction amount of the humidifier spray amount from the spray water amount of the intake spray device From the correction amount calculator, the amount of spray water of the humidifier, the humidifier outlet maximum water vapor amount calculated by the humidifier outlet maximum water vapor amount calculator, and the humidifier spray amount correction amount calculated by the humidifier spray amount correction amount calculator A humidifier outlet water vapor amount calculator for calculating the humidifier outlet water vapor amount, a humidifier outlet humidity calculator for calculating the humidifier outlet humidity from the humidifier outlet water vapor amount calculated by the humidifier outlet water vapor amount calculator, and a gas Gas turbine fuel excellent in flame holding performance from the combustion air flow rate of the combustion air supplied to the turbine combustor and the humidifier outlet humidity calculated by the humidifier outlet humidity calculator A combustion temperature F1 gain calculator and a humidity F1 gain calculator for calculating a control gain for the combustion temperature and humidity for the fuel ratio of the fuel supplied to the combustion section of the combustor are provided, and these combustion temperature F1 gain calculator and humidity F1 gain are provided. Based on the calculation value of the calculator, the fuel flow ratio setting device sets the fuel ratio of the fuel supplied to the combustion portion having excellent flame holding properties among the plurality of combustion portions provided in the gas turbine combustor. A fuel control device for a gas turbine combustor installed in a high-humidity air-utilizing gas turbine, wherein a flow rate ratio of fuel supplied to a plurality of combustion sections of the gas turbine combustor is controlled.

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